Performance improvement of the combat aircraft/engine unit rests on the optimization of intake/engine compatibility. This optimization requires specific flight tests in which the loss of the pumping margin of the compressors due to distortion is determined. The general methodology for the intake/engine compatibility analysis is described from the first wind tunnel tests to the flight tests. In order to determine the loss of the pumping margin due to the distortion of the air intake, an extensive instrumentation set was installed on the Mirage 2000 (Dassault Aviation) aircraft equipped with the M53-P2 (SNECMA) engine. The test procedures as well as the processing of the nonstationary signals are described. The correlations binding the nonstationary coefficients of distortion to the loss of pumping margin of the low pressure compressor are presented. It is shown that a correlation to only one parameter makes it possible to reach an accuracy of plus or minus 2 percent. On the other hand, the use of a correlation of two parameters (circumferential and radial) makes it possible to reduce the precision to plus or minus 1 percent. The use of an engine test stand in an altitude chamber with channels simulating nonstationary distortion makes it possible to reproduce in a satisfactory way the phenomena observed in flight and, in particular, to measure values of sensitivity to the distortion similar to the values obtained in flight. This method makes it possible to improve the optimization of the engine while reducing the number of flight tests.
Analyse en Vol de la Compatibilite Entree d'Air-Moteur (Flight Analysis of Air Intake/Engine Compatibility)
1992
12 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Compatibility , Compressor efficiency , Engine airframe integration , Engine inlets , Flight tests , Mirage aircraft , Wind tunnel tests , Engine tests , Altitude simulation , Distortion , Engine design , Flow characteristics , Sensitivity , Surges , Test stands , Foreign technology
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